Introduction
Nowadays, the drones' industry has created entirely new markets, with new unprecedented opportunities. Drones are used today in many applications; for instance, they are exploited in: disaster management (search and rescue, firefighting etc.), wildlife, weather and environmental monitoring, thermal infrared for power line, gas and oil pipe surveillance, rural medical services, exploration, law enforcement, military operation and surveillance, television news coverage, aerial imaging, traffic monitoring, etc. According to a market research investigation, the drones' industry will result in an economic impact of around 82 billion USD between 2015 and 2025, only in USA.

Even if the main concepts, that underlie hovering, taking off, flying and landing, are similar for all different types of drones (see Figure 1), it proves to be very difficult to build a dynamical model for such systems. Mainly, these difficulties are generated by (1) the nonlinear characteristics of these specific types of equipment, as well as, by (2) the constructive diversity of drones. The parameters of the drone's dynamical model are directly correlated with the parameters of the software control system (i.e., the parameters of the Kalman filter and PID  see Figure 2). Because only part of the control parameters can be roughly estimated, a trial and error procedure is required in order to properly tune all control parameters; this tuning is done accordingly with the best dynamical flying characteristic imposed by: (1) the requirements of the owner and (2) the specific domain of use (e.g. acrobatic versus surveillance).
Figure 2.
The quadcopter’s main software architecture

Application Overview
The system used is a fourrotor Unmanned Air Vehicle (UAV) called quadcopter, Figure 3. The electronics that control and command the quadcopter consists of: (1) a flight stabilizer sensor, which is a nine degree of freedom (gyroscope, accelerometer and compass) Inertial Measurement Unit (IMU) – MPU9250, (2) a 32 bits microcontroller, working at 80 MHz – PIC32MX695F512H and (3) a Bluetooth module.
Apparently, from a conceptual point of view obtaining the pitch and roll angles is a matter of being able to read the accelerometer, convert these readings to the g unit and apply the corresponding equations. But, the accelerometers are not very accurate  they are easily affected by vibrations. To understand how much accelerometers are affected by vibration, I present a small film below.
Apparently, from a conceptual point of view obtaining the pitch and roll angles is a matter of being able to read the accelerometer, convert these readings to the g unit and apply the corresponding equations. But, the accelerometers are not very accurate  they are easily affected by vibrations. To understand how much accelerometers are affected by vibration, I present a small film below.
As we can see, from the movie, the quadcopter is on the ground with the engines running  so, the engine speed is not very high (as in the case of a flight) and, therefore, the vibrations induced in the structure are not of maximum values. However, the angle (roll) determined using only the information from the accelerometer sensor has an unreliable behavior  the quadcopter is in a horizontal position, but the determined angle shows us a 180 degree rotation for the quadcopter.
Due to the lack of any prior experience in the control of quadcopter systems, several approaches were previously used. The identification of an unknown parameter for a quadcopter can be done in two main different ways. In the first methodology, the unknown parameter(s) can be determined by direct computation from the quadcopter model. The second way is by analyzing the flight data.
Due to the lack of any prior experience in the control of quadcopter systems, several approaches were previously used. The identification of an unknown parameter for a quadcopter can be done in two main different ways. In the first methodology, the unknown parameter(s) can be determined by direct computation from the quadcopter model. The second way is by analyzing the flight data.
Figure 3. (a) Quadcopter frame 
Figure 3. (b) Electronical control unit 
Prior to the introduction of the software package, proposed
in this paper and developed together with the indicated quadcopter, a
modelbased design approach for the control system of the quadcopter was followed.
The modelbased design approach was created using the following triad:
SimMechanics, Simulink and Matlab. Unfortunately, it was very difficult and
hard to build a realistic 3D CAD model of our quadcopter. As a result of this
difficulty, a different approach had to be followed.
In a first step, a specific application was developed to determine and tune the Kalman filter parameters. The Kalman filter was used to calculate a precise angle (i.e., the roll or pitch angle) within a data sensor fusion process, that combined data from both accelerometer sensor and gyroscope sensor, Figure 2.
The Kalman filter is a recursive estimator, having two
stages: the prediction and the update stage.
Prediction
stage:
I. Predict the state (eq. 1):
II. Compute the predicted error (eq. 2):
III. Sensor prediction (eq. 3):
Update
stage:
IV. Compute the Kalman Gain (eq. 4):
V. Update the estimate with the
measurement (eq. 5):
VI. Update the error covariance (eq. 6):
This paper does not aim to explain how Kalman filter
operates. On the web you will find a lot of very good tutorials that will help you understand the basic concepts of the Kalman filter. For example, you can read/listen to the following tutorials: the one made by Michel van Biezen (video tutorial), Kalman Filter with MATLAB example (a video tutorial, made by Student Dave), pitch and roll estimating Kalman filter for stabilizing quadrocopters (made by LHelge) etc.
The most important step in designing a Kalman filter lies in its
tuning – one of its major problems. Tuning is achieved by carefully selecting
the Q and R covariance matrices, presented in the equations above. Today, there
are some methods to estimate these parameters from data (with some inaccuracy,
that are impossible to know); among these methods, the trial and error method
stands out as the most extensively used method in “tuning” the filter at the
desire performance. Other parameters that are required at the startup of the
algorithm  such as the values for the error covariance matrix of the state, P,
and the state matrix (from equation (1))
 are also unknown.
The most important step in designing a Kalman filter lies in its tuning – one of its major problems. Tuning is achieved by carefully selecting the Q and R covariance matrices, presented in the equations above. Today, there are some methods to estimate these parameters from data (with some inaccuracy, that are impossible to know); among these methods, the trial and error method stands out as the most extensively used method in “tuning” the filter at the desire performance. Other parameters that are required at the startup of the algorithm  such as the values for the error covariance matrix of the state, P, and the state matrix (from equation (1))  are also unknown.
Figure 4. (a) The main UIR 
Figure 4. (c) UIR to set the Kalman Filter parameters 
Aside from these, during the designing process of our
particular drone, we had to take some additional decisions. One of them was
tied to the particular configuration assumed for the quadcopter. In its actual
configuration, the system, Figure
3, uses: (1) two sensors (an
accelerometer and a gyroscope) with (2) two axes each (x and y, Figure
2). From here, many approaches
could be equally followed to construct the state matrix (from equation (1)) – e.g.: (1) to combine all sensors and all axes together, (2) to run the Kalman filter two times
for each axes (as it is presented in Figure
2), (3) to introduce only the angle and the angle bias on the state
matrix or to put also the angular velocity, etc.
In order to choose both the best software architecture and
the optimal parameters for the Kalman filter, a special application was
developed. This application, which communicates with a CC2650 SensorTag placed on
the quadcopter, was designed:
(1) to configure (see Figure 4(a)) and to get the accelerometer, gyroscopic and magnetic data
from the SensorTag, and
(2) to present these data in
different visual formats and/or to save them to the hard drive – see Figure 5(a), (b) and (c).
By setting the different Kalman filter parameters (on a specific panel belonging to the application, see Figure 4. (c)) and testing them on a quadcopter, an incremental improvement of the dynamic regime will be achieved until the desired behavior is reached.
The SensorTag device works as a
GATT server. GATT (Generic Attribute Profile) defines the way that two BLE
(Bluetooth Low Energy) devices transfer data back and forth. The CC2650
SensorTag was selected mainly because it incorporates the same MPU9250 IMU
that we also used in our quadcopter control system, see Figure 3.
Figure 5. (a) Strip Chart graph of the acceleration data 
Figure 5. (b) Strip Chart graph of the gyroscopic data 
Figure 5. (c) the roll angle given by the accelerometer, gyroscope and Kalman filter 
The optimal Kalman filter parameters, obtained with this software package, further feed the Kalman filter implemented with the software programs running inside the PIC32MX695F512H microcontroller.
In the second step, another application was developed and used in order to find the optimal parameters for the PID control loop, Figure 6. The communication between the quadcopter and the personal computer (that was running this software package) was realized by a Bluetooth protocol that tunnels a standard RS232 serial communication protocol. Another contribution of this second software application is that it plays a relay function. More exactly, it receives commands from a Microsoft XBOX wireless controller (i.e., throttle, forwardbackward and leftrights commands) and further sends them to the quadcopter.
Both applications were written in C language, using the LabWindows CVI environment. This environment provides a significant advantage in terms of speed and easiness of software development, deployment and testing. A leading benefit that LabWindows CVI brings consists in its powerful algorithms and functions included in the Advanced Data Analysis library – especially, array operations; this kind of operations were widely used in our both developed applications. The ability to interface and easily work with Windows SDK was the second exploited advantage.
At the beginning, the applications was developed using Microsoft Visual Studio environment. Moving from Microsoft Visual Studio to LabWindows CVI environment was a necessity mainly given: (1) by the need of an easy and fast way to communicate and display the information to the user and, also, (2) by the advantages assured by the RS232 library.
At this moment, in the Microsoft virtual store six applications are able to interface with Texas Instruments SensorTags (CC2541 and/or CC2650). But unfortunately, none of them was designed to determine the optimum parameters of a Kalman filter. All six applications can only configure a SensorTag and present visually the values acquired from the sensors. Comparing these applications with the BLE SensorTag application, Figure 4, we can say, without fail, that it implements entirely new functions (nonexistent in all other applications) which, by their practical applicability, define its value and unicity.
With LabWindows CVI, we built two applications. Using these software packages the development of the drone control unit can be done in an efficient, faster and cheaper way, with a small development team.
The LabWindows CVI meets all our expectations. It gave to us all the flexibility and power to implement and test multiple mathematical models. These models are parts of the drone command and control units. The next logical step in the system development process will be to implement a magnetometer tilt compensation for yaw axis.
At the beginning, the applications was developed using Microsoft Visual Studio environment. Moving from Microsoft Visual Studio to LabWindows CVI environment was a necessity mainly given: (1) by the need of an easy and fast way to communicate and display the information to the user and, also, (2) by the advantages assured by the RS232 library.
Benefits of blessTags application
From our experience, with two previous failed attempts to build control units for drones (a bicopter and a smaller quadcopter), I had to conclude that, without a very flexible set of tools used to tune and test the drone controller unit, it is very difficult and almost impossible to obtain a stabile hovering. The impact of these applications are, therefore, directly related to a significant cut down of the development time and costs.At this moment, in the Microsoft virtual store six applications are able to interface with Texas Instruments SensorTags (CC2541 and/or CC2650). But unfortunately, none of them was designed to determine the optimum parameters of a Kalman filter. All six applications can only configure a SensorTag and present visually the values acquired from the sensors. Comparing these applications with the BLE SensorTag application, Figure 4, we can say, without fail, that it implements entirely new functions (nonexistent in all other applications) which, by their practical applicability, define its value and unicity.
Conclusions
In this paper, the main concept of modeling and controlling a quadcopter was presented. One major advantage of this concept is given by the developed software packages that can be applied to a variety of other systems.With LabWindows CVI, we built two applications. Using these software packages the development of the drone control unit can be done in an efficient, faster and cheaper way, with a small development team.
The LabWindows CVI meets all our expectations. It gave to us all the flexibility and power to implement and test multiple mathematical models. These models are parts of the drone command and control units. The next logical step in the system development process will be to implement a magnetometer tilt compensation for yaw axis.
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